Planetary spacecraft - SEPS interface designThe interactions between a spacecraft which would rendezvous with the comet Tempel II, the stage, and the mission design are summarized along with solar electric propulsion system design issues. Attention is given to data communication, the spacecraft pointing control system, spacecraft power, plasma interactions, the release of a probe to study the comet Halley, and thruster usage. It was concluded that for a planetary mission design using a low-thrust stage, the control of the mission should reside in the payload spacecraft and that the power should be provided by the stage; the NASA standard 28 VDC bus is recommended.
Document ID
19800057347
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pless, L. C. (California Institute of Technology, Jet Propulsion Laboratory, Electric Propulsion and Advanced Concepts Group, Pasadena Calif., United States)